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TECHNICAL PAPERS

Shock Wave–Film Cooling Interactions in Transonic Flows

[+] Author and Article Information
P. M. Ligrani

Convective Heat Transfer Laboratory, Department of Mechanical Engineering, University of Utah, Salt Lake City, UT 84112

C. Saumweber, A. Schulz, S. Wittig

Lehrstuhl und Institute für Thermische Stroemungsmaschinen, Universitaet Karlsruhe (T.H.), Kaiserstrasse 12, D-76128 Karlsruhe, Germany

J. Turbomach 123(4), 788-797 (Feb 01, 2001) (10 pages) doi:10.1115/1.1397305 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

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Popp, O., Smith, D. E., Bubb, J. V., Grabowski, H., III, Diller, T. E., Schetz, J. A., and Ng, W. F., 2000, “Investigation of Heat Transfer in a Film Cooled Transonic Turbine Cascade, Part II: Unsteady Heat Transfer,” ASME Paper No. 2000-GT-203.
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Figures

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Schematic diagram showing: (a) overall arrangement of the experimental facility, and (b) a cut-away view of the test section
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Schematic diagram of shadowgraph flow visualization apparatus
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Discharge coefficients as dependent upon ratio of coolant to mainstream pressure, mainstream Mach number, and coolant passage Mach number.

Spanwise Inclination hole Study angle ml/dρcMMcspacing —•— Present study 30° 0.49 6 1.59 0.8 0 4 d—▵— Gritsch et al. 14 30° 0 .626 1.85 0.6 0 — —○— Schmidt et al. 34 35° 0.63 4 1.60 <0.1 0 3 d—⋄— Bell et al. 35 35° 0.70 3 1.39 <0.1 0 3 d

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Comparisons of adiabatic film cooling effectiveness data from the present study to results from other investigations: (a) Comparison of centerline data with results from Gritsch et al. 14 and Schmidt et al. 34. (b) Comparison of spanwise-averaged data with results from Schmidt et al. 34 and Bell et al. 35.
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Local surface adiabatic film cooling effectiveness distribution for m=0.49,M=0.80, and an injectant plenum condition giving MC=0.0
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Local surface adiabatic film cooling effectiveness distribution for m=0.53,M=1.12, and an injectant plenum condition giving Mc=0.0. Scale for contour map is given in Fig. 5.
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Local surface adiabatic film cooling effectiveness distribution for m=1.48,M=1.12, and an injectant plenum condition giving MC=0.0. Scale for contour map is given in Fig. 5.
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Local surface adiabatic film cooling effectiveness distribution for m=0.54,M=1.10, and perpendicular injectant crossflow with MC=0.30. Scale for contour map is given in Fig. 5.
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Local centerline surface adiabatic film cooling effectiveness values for the same experimental conditions as for the results in Figs. 5678
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Local midspan surface adiabatic film cooling effectiveness values for the same experimental conditions as for the results in Figs. 5678. Symbol lables are given in Fig. 9.
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Adiabatic film cooling effectiveness distributions for different M and m, with a plenum injectant condition with Mc=0: (a) spanwise-averaged values; (b) centerline values; (c) midspan values
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Shadowgraph flow visualization images for M=1.12 and MC=0: (a) m=0.53; (b) m=0.98; (c) m=1.48. Arrows denote mainflow direction.
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Adiabatic film cooling effectiveness distributions for different M and m, with perpendicular injectant crossflow with MC=0.3: (a) Spanwise-averaged values; (b) centerline values; (c) midspan values
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Shadowgraph flow visualization images for M=1.10 and MC=0.30: (a) m=0.32; (b) m=0.54. Arrows denote mainflow direction.
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Adiabatic film cooling effectiveness distributions for different M and MC, for m=0.5: (a) spanwise-averaged values; (b) centerline values; (c) midspan values
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Shadowgraph flow visualization images for M=1.10–1.12 and m=0.5: (a) Mc=0; (b) MC=0.15; (c) MC=0.30; (d) Mc=0.59. Arrows denote mainflow direction.

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